IL268133B - Vtol aircraft having ducted thrust from a central fan - Google Patents

Vtol aircraft having ducted thrust from a central fan

Info

Publication number
IL268133B
IL268133B IL268133A IL26813319A IL268133B IL 268133 B IL268133 B IL 268133B IL 268133 A IL268133 A IL 268133A IL 26813319 A IL26813319 A IL 26813319A IL 268133 B IL268133 B IL 268133B
Authority
IL
Israel
Prior art keywords
vtol aircraft
duct
main body
upper shell
nozzle
Prior art date
Application number
IL268133A
Other languages
Hebrew (he)
Other versions
IL268133A (en
Inventor
Maran John Vedamanikam
Original Assignee
Maran John Vedamanikam
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Maran John Vedamanikam filed Critical Maran John Vedamanikam
Publication of IL268133A publication Critical patent/IL268133A/en
Publication of IL268133B publication Critical patent/IL268133B/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068—Fuselage sections
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
    • B64C29/0066—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors with horizontal jet and jet deflector
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/20—Vertical take-off and landing [VTOL] aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/70—Constructional aspects of the UAV body
    • B64U20/75—Constructional aspects of the UAV body the body formed by joined shells or by a shell overlaying a chassis
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
  • Fats And Perfumes (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Description

PCT/US2018/014596 WO 2018/136844 VTOL Aircraft Having Ducted Thrust From A Central Fan Cross-References to Related Applications This application claims priority from U.S. Provisional Application Serial Number 62/448,8 filed January 20, 2017, which is hereby incorporated herein by reference in its entirety.
Field of the Invention The present invention relates to a multi-ducted centrifugal fan VTOL aircraft.
Background of the Invention Currently-available VTOL drone aircrafts are of the multi-rotor type that suffer from limited flight time and payload capacity due to two main reasons: their electrical operation which requires heavy batteries that must be recharged over a period of time, and the inefficiency of the use of rotors or propellers that do not provide high amounts of overall lift. They cannot accommodate the use of fuel (e.g. gasoline) for quick mission turnaround time and must use additional pre-charged batteries. The weight of the batteries limits the amount of payload they can carry, as well as the operational flight time, because batteries do not have a high energy capacity in relation to their weight like fuel does. The current aircraft typically have exposed rotors or propellers that create safety hazards to personnel and property.
It is thus an aim of the present invention to address at least one of these issues.
Brief Description of the Figures Fig. 1 depicts an aspect of a VTOL aircraft of the invention.
Fig. 2 depicts a bottom view of the VTOL aircraft of the invention.
Fig. 3 depicts a top view of the VTOL aircraft of the invention.
PCT/US2018/014596 WO 2018/136844 Fig. 4 depicts an exploded view of the VTOL aircraft of the invention.
Fig. 5 depicts a bottom view of the VTOL aircraft of the invention.
Fig. 6 depicts a top view of the VTOL aircraft of the invention.
Fig. 7 depicts a cross-sectional view of the VTOL aircraft of the invention.
Fig. 8 depicts a perspective bottom view of a two outlet VTOL aircraft.
Fig. 9 depicts a perspective top view of a two outlet VTOL aircraft.
Brief Summary of the Embodiments of Invention A VTOL aircraft having thrust and directional control comprises a main body. The main body has an upper shell in a shape of a parabola, with the shape of a parabola facing and expanding into a downward-facing end. The upper shell of the main body has a top opening in a shape of a circle. The main body also has a bottom plate in a shape of a flat circle, sealed to the downward- facing end of the upper shell of the main body. The top opening of the upper shell of the main body provides an inlet for air to enter into the housing. The upper shell of the main body has at least one opening.
A fan provides a centrifugal flow of air. The fan has a central hub, and a plurality of blades extends radially outward from the central hub. The fan is mounted to the bottom plate of the main body.
At least one duct allows and directs air flow. At least one nozzle allows for exhaust release.
Each nozzle is attached one each of the ducts. Each nozzle has a turn measuring 90° and facing downward from its respective duct. Each nozzle has an end at which is a vane for redirecting airflow.
PCT/US2018/014596 WO 2018/136844 Detailed Description of the Embodiments of the Invention First depicted in Fig. 1, a VTOL aircraft 20comprises a housing 25.The housing 25 comprises a main body 30.The main body 30has an upper shell 35in a shape of a parabola, with the shape of a parabola facing and expanding into a downward-facing end 35a.The upper shell 35 of the main body 30has a top opening 40in a shape of a circle. The main body 30also has a bottom plate 45in a shape of a flat circle, sealed to the downward-facing end 35aof the upper shell 35of the main body 30.The bottom plate 45has a top side 45a(Fig. 4) and a bottom side 45b(Fig. 2). The top opening 40of the upper shell 35of the main body 30provides an inlet for air to enter into the housing 25.The upper shell 35of the main body 30has at least one opening 50,for instance a set of four openings 50.The set of four openings 50each has a shape of an oval.
As illustrated in Fig. 3, each of the set of four openings 50is placed around the upper shell 35of the main body 30at 90° to each other.
A fan 55(Fig. 6) provides a centrifugal flow of air. The fan 55has a central hub 60(Fig. 6), and a plurality of blades 65(Fig. 6) extends radially outward from the central hub 60.The fan 55is mounted to the top side 45aof the bottom plate 45of the main body 30.An attachment 120 for landing the VTOL aircraft 20is attached to the bottom side 45bof the bottom plate 45of the main body 30,as depicted in Figs. 5 and 7.
At least one duct 70(Figs. 1 and 3), for instance a group of four ducts 70,allows and directs air flow. Each of the group of four ducts 70has a cross-section having a shape of an oval. Each of the group of four ducts 70has a first end 75and a second end 80.The first end 75of each of the group of four ducts 70fits into one of the set of four openings 50,and the second end 80of each of the group of four ducts 70extends horizontally outward therefrom. Each of the group of four ducts 70has a width 85and a height 90(Figs. 1 and 3). The width 85of each of the group of four PCT/US2018/014596 WO 2018/136844 ducts 70 decreases from the first end 75 to the second end 80 of each of the group of four ducts 70. The height 90 of each of the group of four ducts 70 remains constant from the first end 75 to the second end 80 of each of the group of four ducts 70.
As illustrated in Figs. 4 and 7, at least one nozzle 100, for instance, a group of four nozzles 100, allows for exhaust release. Each of the group of four nozzles 100 has a cross-section having a shape of an oval. Each of the group of four nozzles 100 has a first end 105 attached to the second end 80 of one of each of the group of four ducts 70. Each of the group of four nozzles 100 has a turn 115 (Figs. 4 and 7) measuring 90° and facing downward from the second end 80 of each of the group of four ducts 70. Each of the group of four nozzles 100 has a second end 110 at which is a vane 95 for redirecting airflow.
In a variant, the size of the top opening 40 of the main body 30 is 87.5% of the size of the fan 55. Each of the four ducts 70 is 15.6% of the size of the top opening 40 of the main body 30.
Each of the second ends 80 of each duct 70 is 50% of the size of the first ends 75 of each duct 70.
Each of the second ends 80 of each duct 70 is 7.8% of the size of the top opening 40 of the main body 30.
In another variant, depicted in Figs. 8 and 9, a VTOL aircraft 200 comprises exactly two outlets for thrust. The VTOL 200 has a housing 25 and comprises a main body 30. The main body has an upper shell 35 in a shape of a parabola, with the shape of a parabola facing and expanding into a downward-facing end 35a. The upper shell 35 of the main body 30 has a top opening 40 in a shape of a circle. The main body 30 also has a bottom plate 45 in a shape of a flat circle, sealed to the downward-facing end 35a of the upper shell 35 of the main body 30. The top opening 40 of the upper shell 35 of the main body 30 provides an inlet for air to enter into the housing 25. The upper shell 35 of the main body 30 has two openings 50. The set of two openings 50 each has a PCT/US2018/014596 WO 2018/136844 shape of an oval. Each of the two openings 50is placed around the upper shell 35of the main body 30at 180° to each other, facing each other.
As with the previous variant, a fan provides a centrifugal flow of air, similar to Fig. 6. The fan has a central hub, and a plurality of blades extends radially outward from the central hub. The fan is mounted to the top side of the bottom plate 45of the main body 30.
Two ducts 70allow and directs air flow. Each of the ducts 70has a cross-section having a shape of an oval. Each of the ducts 70has a first end 75and a second end 80.The first end 75fits into one of the set of the openings 50,and the second end 80of each extends horizontally outward therefrom. Each of the ducts 70has a width and a height 90.The width remains constant from the first end 75to the second end 80of each duct 70.The height 90of each of the ducts 70remains constant from the first end 75to the second end 80of each of the ducts 70.Similar to Figs. 4 and 7, at least one nozzle 100,allows for exhaust release. Each of the nozzles 100has a cross-section having a shape of an oval. Each of the nozzles 100has a first end 105attached to the second end

Claims (17)

1./ CLAIMS 1. A VTOL aircraft having thrust and directional control, comprising: a housing; a fan for providing a centrifugal flow of air; at least one duct for directing air flow; at least one nozzle in fluid communication with and connected to the duct, for expelling air flow; wherein the housing comprises a main body; the main body has an upper shell in a shape of a parabola, the shape of a parabola faces and expands into a downward-facing end; the upper shell of the main body has a top, substantially circular opening; the main body also has a bottom plate sealed to the downward-facing end of the upper shell of the main body; the bottom plate having a top side and a bottom side; and the top opening of the upper shell of the main body provides an inlet for air to enter into the housing.
2. The VTOL aircraft of claim 1, wherein: the fan has a central hub; and the fan has a plurality of blades extending radially outward from the central hub.
3. The VTOL aircraft of claim 1, wherein each of the at least one duct has a cross-section having a shape of an oval.
4. The VTOL aircraft of claim 1, wherein each of the at least one nozzle has a cross-section having a shape of an oval.
5. The VTOL aircraft of claim 1, wherein: each of the at least one duct has a width and a height; 268133/ the width of each of the at least one duct decreases from the first end to the second end of each of the at least one duct; and the height of each of the at least one duct remains constant from the first end to the second end of each of the at least one duct.
6. The VTOL aircraft of claim 1, wherein: each of the at least one nozzle has a first end attached to the second end of one of each of the at least one duct; each of the at least one nozzle has a turn measuring 90° and faces downward from the second end of each of the at least one duct; and each of the at least one nozzle has a second end at which is at least one vane for redirecting airflow, with the vane having a curvature.
7. The VTOL aircraft of claim 1, wherein the at least one duct is a group of four ducts.
8. The VTOL aircraft of claim 1, wherein the at least one nozzle is a group of four nozzles.
9. The VTOL aircraft of claim 1, further comprising an attachment to the bottom side of the bottom plate, to allow the VTOL aircraft to land.
10. The VTOL aircraft of claim 1, wherein: the upper shell of the main body has at least opening; the at least one opening has a shape of an oval; and each of the at least one opening is placed around the upper shell of the main body at 90° to each other.
11. The VTOL aircraft of claim 1, wherein: each of the at least one duct has a first end and a second end; the first end of each of the at least one duct fits into one of the at least one opening; and the second end of each of the at least one duct extends horizontally outward therefrom. 268133/
12. The VTOL aircraft of claim 2, wherein the fan is mounted to the top side of the bottom plate of the main body.
13. The VTOL aircraft of claim 7, wherein the at least one vane is a group of three vanes.
14. The VTOL aircraft of claim 11, wherein the at least one opening is a set of four openings.
15. The VTOL aircraft of claim 1, wherein the at least one duct is a group of exactly two ducts.
16. The VTOL aircraft of claim 1, wherein the at least one nozzle is a group of exactly two nozzles.
17. The VTOL aircraft of claim 11, wherein the at least one opening is a set of two openings.
IL268133A 2017-01-20 2018-01-20 Vtol aircraft having ducted thrust from a central fan IL268133B (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201762448891P 2017-01-20 2017-01-20
PCT/US2018/014596 WO2018136844A1 (en) 2017-01-20 2018-01-20 Vtol aircraft having ducted thrust from a central fan

Publications (2)

Publication Number Publication Date
IL268133A IL268133A (en) 2019-09-26
IL268133B true IL268133B (en) 2022-08-01

Family

ID=62905932

Family Applications (1)

Application Number Title Priority Date Filing Date
IL268133A IL268133B (en) 2017-01-20 2018-01-20 Vtol aircraft having ducted thrust from a central fan

Country Status (6)

Country Link
US (2) US20190367165A1 (en)
EP (1) EP3589541A4 (en)
CA (1) CA3051220A1 (en)
GB (1) GB2575565B (en)
IL (1) IL268133B (en)
WO (1) WO2018136844A1 (en)

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CN106314777B (en) * 2016-08-29 2019-12-24 英华达（上海）科技有限公司 Unmanned aerial vehicle
US10583924B2 (en) * 2017-10-01 2020-03-10 Petru A. Simionescu Vertical takeoff and landing unmanned aerial vehicle (VTOL-UAV)
US11396888B1 (en) 2017-11-09 2022-07-26 Williams International Co., L.L.C. System and method for guiding compressible gas flowing through a duct
US11591087B2 (en) * 2019-04-07 2023-02-28 Donald Lee Chalker Unmanned aerial vehicle with ducted rotors
USD870017S1 (en) * 2019-05-03 2019-12-17 Xiao Meng Aircraft
WO2021034783A1 (en) * 2019-08-19 2021-02-25 Mark Holtzapple Enhanced-thrust lift and propulsion systems
WO2021212357A1 (en) * 2020-04-22 2021-10-28 深圳市大疆创新科技有限公司 Unmanned aerial vehicle

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Also Published As

Publication number Publication date
IL268133A (en) 2019-09-26
US10106254B2 (en) 2018-10-23
EP3589541A1 (en) 2020-01-08
US20180208304A1 (en) 2018-07-26
CA3051220A1 (en) 2018-07-26
EP3589541A4 (en) 2021-01-13
WO2018136844A1 (en) 2018-07-26
GB2575565A (en) 2020-01-15
US20190367165A1 (en) 2019-12-05
GB2575565B (en) 2022-07-20
GB201911962D0 (en) 2019-10-02

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